US4400934A - Gas turbine unit with auxiliary devices and a compressed air branch or gas under pressure - Google Patents
Gas turbine unit with auxiliary devices and a compressed air branch or gas under pressure Download PDFInfo
- Publication number
- US4400934A US4400934A US06/184,430 US18443080A US4400934A US 4400934 A US4400934 A US 4400934A US 18443080 A US18443080 A US 18443080A US 4400934 A US4400934 A US 4400934A
- Authority
- US
- United States
- Prior art keywords
- output
- operating fluid
- pressure
- compressed air
- improvement
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 239000012530 fluid Substances 0.000 claims description 23
- 238000013022 venting Methods 0.000 claims description 7
- 239000000446 fuel Substances 0.000 claims description 5
- 230000001050 lubricating effect Effects 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 claims 1
- 239000000314 lubricant Substances 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000006073 displacement reaction Methods 0.000 abstract description 22
- 230000005540 biological transmission Effects 0.000 abstract description 8
- 230000001939 inductive effect Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
Definitions
- the present invention relates to a gas turbine unit with auxiliary devices and, in the region of the compressor, a compressed air branch, or gas under pressure for the operation of the gas turbine.
- Gas turbine units are generally known with these features. Units directly required for operation of the gas turbine unit comprise the auxiliary devices, including the fuel feeding or injection pump, the lubricating oil pump, as well as units such as a hydraulic pump for the regulator or control, an auxiliary generator, and the like, depending upon the use or application involved. None of these units, with a conventional embodiment, has an operating speed in the region of the gas turbine speed. For the mechanical drive of the auxiliary devices, therefore, a suitable transmission must be provided which in turn provides a number of branches corresponding to the variously required speed reductions. The gas turbine unit accordingly must be expanded by a costly gearing having a drive which must be taken into consideration already during the construction of the gas turbine.
- the transmission is concerned with each change of auxiliary devices, and requires high-value structural parts because of the high speed.
- Compressed air branches in the region of the compressor, with the known gas turbine units, are provided for heating purposes or, in connection with expansion members, for cooling purposes.
- the speed measurement occurs in part by means of an inductive emitter, and starting occurs by subjecting impeller wheels with independently generated compressed air.
- the previous conventional costly apparatus support with speed reduction and branch transmissions is thereby made superfluous.
- the previously known functions of the compressed air branching are to remain unrestricted.
- the gas turbine unit under these circumstances is to be capable of being used in stationary installations, for instance as industrial gas turbines, as well as in non-stationary or mobile installations, for instance as a jet drive.
- FIG. 1 shows a pressure exchanger and two separate pump units
- FIG. 2 shows a pressure exchanger with a cylinder having a graduated or stepped cross section and two integrated pump units.
- the gas turbine unit of the present invention is characterized primarily in that compressed air branched off from the compressor, or gas under pressure, serves for direct drive of an energy exchanger which, while avoiding transmissions and the like otherwise needed for this purpose, generates the oscillating or rotating movement necessary for driving the auxiliary apparatus of the gas turbine unit or the entire configuration formed therewith.
- the energy inherent in the compressed air or in the gas is converted into the necessary movement for driving the auxiliary devices, with conversion occurring in an energy exchanger at a location advantageous for the arrangement of an auxiliary device.
- the size of the driven energy exchanger can be kept very small with branching-off of highly compressed pressurized or compressed air, or with removal of gas from a high-pressure system.
- the energy exchanger depending upon the pressure and quantity conditions of the medium, can be a piston or flow machine. All mechanically driven machines are operable as auxiliary devices, especially also piston or flow machines, whereby in a special case an auxiliary device can generate a pressure medium for driving a further unit.
- advantageous is the flexibility in relation to the selection and arrangement of the auxiliary devices as gained with the present invention.
- the energy is converted to the pressure increase of media in an especially advantageous manner in an energy exchanger with auxiliary devices in the form of piston pumps; these media, for instance pressure oil for lubricating purposes, and fuel, are necessary directly for the operation of the gas turbine unit or machine system formed therewith.
- a partial flow of the media can serve as working medium for the drive of further auxiliary devices.
- the transmission is replaced by a structurally considerably simpler apparatus unit which simultaneously takes over the function of the previously necessary fuel and lubricating-oil pumps.
- Simple hydraulic work machines can be additionally arranged as further auxiliary devices.
- An especially advantageous embodiment of an energy exchanger embodied as a unit and having two auxiliary devices provides a double-acting working cylinder unit and two likewise double-acting displacement cylinder units, the three pistons of which are connected with a coaxial piston rod.
- the individual cylinder cross sections are designed to the pressures or conveying quantities of the conveyed media, i.e., preferably fuel and lubricating oil.
- Respective working chambers are formed in the cylinder units by the respective pistons with the two stationary cylinder end walls, so that a displacement procedure occurs during piston movement in both directions.
- a cylinder with a graduated or stepped cross section is used in unison with an energy exchanger embodied with two auxiliary devices in an embodiment simplified in an advantageous manner and in which four cylinder chambers are formed by three pistons connected with a piston rod.
- This embodiment can be considered as advantageous if only one medium is to be conveyed. In this case, a displacement effect is provided again with piston movement in both directions.
- control of the piston movement can be effected by two coupled 3/2-way valves which in an inventive embodiment are automatically reversed or changed over as magnetic valves by an inductive displacement pickup in the end positions of the pistons.
- gas turbine units which are operated with gas
- the gas under high pressure can in this case inventively take the place of the compressed air branched off from the compressor and can be utilized for pressure oil conveying.
- FIG. 1 shows a compressed air branch 21 which, after leaving the compressor 1, leads to a 3/2-way valve 12 embodied in a double manner of construction.
- the control slide 17s connects one of the supply lines 16 which leads to the working cylinder 3 on the input side of the pressure transducer with the compressed air branch 21, and connects the other supply line 16 which leads to the working cylinder 3 with one of the venting lines 15.
- Two changeable or variable working cylinder chambers 32, 33 are formed in the working cylinder 3 by the opposed working surfaces of the power piston 18, which is connected by the piston rod 17 with the driven pistons 19, 20 of the displacement output cylinders 5,8.
- the pistons 19,20 respectively form two displacement cylinder chambers 30, 31.
- Suction lines 23, 24 lead from the storage or collecting containers which contain an operating fluid to the displacement cylinder chambers 30, 31 of the displacement cylinders 5,8, from where output or pressure lines 27, 28 lead to the consuming devices over pressure equalizing containers 6,9.
- Check valves or flaps 10 are arranged in the suction and pressure lines 23, 24, 27, 28.
- the 3/2-way valve 12' has a control slide 17s' with plate seats and a control magnet 13.
- the pressure or energy exchanger 2' has a cylinder 22 of graduated or stepped cross section, in which the working piston 18', with the displacement pistons 19',20' and the folded bellows 35, 36, forms the changeable or variable working cylinder chambers 32', 33'.
- Inductive displacement pickups 14 are arranged on the cylinder 22; they deliver a switching pulse when the displacement pistons 19', 20' approach the walls of the cylinder 22. This switching pulse reverses the control magnet 13 of the 3/2-way valve 12.
- the displacement cylinder chambers 30', 31' are formed with the cylinder 22 by the displacement pistons 19', 20' and the folded bellows 35.
- the lines and control elements correspond to those illustrated in FIG. 1.
- the present invention provides a gas turbine unit with auxiliary devices and, in the region of the compressor, a compressed air branch, or gas under pressure for the operation of the gas turbine.
- Compressed air branched off from the compressor 1, or gas under pressure serves for direct drive of an energy exchanger or pressure transducer 2 which, while avoiding transmissions and the like otherwise needed for this purpose, generates the oscillating or rotating movement necessary for driving the auxiliary devices of the gas turbine unit or the entire system formed therewith.
- the energy exchanger or pressure transducer 2 has working cylinder chambers 32, 33, on the input side and the associated auxiliary apparatus, embodied as pumps, has displacement cylinder chambers 30, 31, on the output side in which chambers pistons 18, 19, 20 embodied in one piece or connected rigidly with each other are arranged axially movable, whereby in the working cylinder chambers 32, 33 there is located the compressed air branched off from the compressor 1 or the gas under pressure, and in the displacement cylinder chambers 30, 31 there is located a medium to be conveyed and intended for the gas turbine or for the entire system formed therewith.
- the input side 32,33 and output side 30,31 are isolated from one another by the walls through which the piston rod 17 passes.
- the energy exchanger and the associated auxiliary devices are constructed comprising a working cylinder 3 and preferably two displacement cylinders 5,8 in each of which a respective piston 18, 19, 20, which are connected rigidly by a common coaxial piston rod 17, forms two changeable or variable cylinder chambers 30, 31; 32, 33 which are connected at the working cylinder 3 with a pressure line 21 for the compressed air branched off from the compressor 1 and the gas under pressure, and a respective venting line 15;
- the cylinder chambers at the displacement cylinders 5,8 have a respective suction line 23, 24 and a pressure line 27, 28, and on the suction side are connected to a supply or collecting container of the medium to be conveyed, and on the pressure side are connected by pressure equalization containers 6,9 to lines to the gas turbine and/or to the entire system formed therewith.
- the energy exchanger 2 and the associated auxiliary devices, embodied as pumps, are constructed as a unit comprising one cylinder 22, of graduated or stepped cross section, in which three pistons 18', 19', 20' are rigidly connected with each other by a coaxial piston rod 17 to form four changeable or variable cylinder chambers, two of which are working cylinder chambers 32', 33' having volumes changing counter to each other and are respectively connected with a pressure line 21 for the compressed air branched off from the compressor 1 or the gas under pressure, and each have a connection with a venting line 15; and the two other chambers of which are displacement cylinder chambers 30', 31' respectively having a connection to a suction connection 23, 24 and a pressure connection 27,28, and on the suction side are connected to the supply or collecting container of the medium to be conveyed, and on the pressure side are connected by pressure equalization containers 6,9 to lines to the gas turbine and/or to the entire system formed therewith.
- the piston rod 17 has axial guides, and the labyrinth seals are arranged on the periphery of the driven pistons 18, 19, and power piston 20 and seal the cylinder chambers 30, 31; 32, 33 relative to each other.
- Foldable bellows 35, 36 which are coaxial with respect to the piston rod 17', on the one hand are connected in the vicinity of the periphery to the pistons 18', 19', 20', and on the other hand are connected to the transverse walls of the cylinders, and seal off or isolate the cylinder chambers 30', 31'; 32',33' with respect to each other.
- a 3/2-way valve 12 embodied in a double or dual manner of construction with a common inlet connection to the pressure line 21 for the compressed air branched off from the compressor 1, or for the gas under pressure, is respectively connected with an outlet connection to a supply line 16 to a working cylinder chamber 22, 23 of the pressure exchanger 2, and is respectively connected with a venting connection to the venting line 15; furthermore, the 3/2-way valve 12, in both positions of its control slide 17s, respectively alternately connects one supply line 16 with the pressure line 21, and the other supply line 16 with a venting line 15.
- the 3/2-way valve 12' may be embodied as a magnetic valve, with an inductive displacement or pickup 14 being arranged on the driven piston, 19', and power piston 20' or the piston rod 17' of the pressure exchanger 2' and giving off a control pulse or signal in the end positions of the pistons 18', 19', 20' by way of electrical connection with the control magnet 13 of the 3/2-way valve 12.
- the energy exchanger 2 has working chambers, and the associated auxiliary apparatus, embodied as pumps, has displacement chambers, in which chambers rotors, turbines, or pistons embodied in one piece or connected rigidly with each other are rotatably arranged, whereby located in the working chambers is the compressed air branched off from the compressor 1 or the gas under pressure, and located in the displacement chambers is a medium to be conveyed and intended for the gas turbine or for the entire system formed therewith.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Compressors, Vaccum Pumps And Other Relevant Systems (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19792936005 DE2936005A1 (de) | 1979-09-06 | 1979-09-06 | Gasturbineneinheit mit hilfsaggregaten und druckluftabzweigungen oder unter druck anstehendem gas |
DE2936005 | 1979-09-06 |
Publications (1)
Publication Number | Publication Date |
---|---|
US4400934A true US4400934A (en) | 1983-08-30 |
Family
ID=6080191
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US06/184,430 Expired - Lifetime US4400934A (en) | 1979-09-06 | 1980-09-05 | Gas turbine unit with auxiliary devices and a compressed air branch or gas under pressure |
Country Status (4)
Country | Link |
---|---|
US (1) | US4400934A (de) |
EP (1) | EP0025526B1 (de) |
CA (1) | CA1162061A (de) |
DE (1) | DE2936005A1 (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5285626A (en) * | 1992-03-20 | 1994-02-15 | Woodward Governor Company | Drive for main engine auxiliaries for an aircraft gas turbine engine |
US5784812A (en) * | 1994-07-13 | 1998-07-28 | O&K Orenstein & Koppel Ag | Method of controlling the positioning of an outfit tilting cylinder mounted on the descending lift frame of movable construction machines |
WO2010089769A2 (en) * | 2009-01-13 | 2010-08-12 | Dattatraya Rajaram Shelke | A device for transferring energy between fluids |
WO2012042533A2 (en) * | 2010-09-29 | 2012-04-05 | Dattatraya Rajaram Shelke | Device for transferring energy between two fluids |
CN103615365A (zh) * | 2013-11-26 | 2014-03-05 | 浙江理工大学 | 一种集成阀式气驱液增压泵 |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3502578A1 (de) * | 1985-01-26 | 1986-07-31 | Klöckner-Humboldt-Deutz AG, 5000 Köln | Hilfsantrieb fuer ein gasturbinentriebwerk |
DE3515770A1 (de) * | 1985-05-02 | 1986-11-06 | Klöckner-Humboldt-Deutz AG, 5000 Köln | Hilfsantriebsanordnung mit getriebe fuer ein gasturbinentriebwerk |
DE29706074U1 (de) * | 1997-04-07 | 1997-07-31 | WiWa Wilhelm Wagner GmbH & Co KG, 35633 Lahnau | Dosierpumpe |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3659417A (en) * | 1968-08-08 | 1972-05-02 | Daimler Benz Ag | Gas turbine unit for generating mechanical energy and compressed air |
US4182117A (en) * | 1978-01-09 | 1980-01-08 | Avco Corporation | Diffuser vane cusp bleed aperture with automatic ejector control device |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2778312A (en) * | 1950-06-10 | 1957-01-22 | Bendix Aviat Corp | Fluid pump and controls therefor |
GB718694A (en) * | 1951-05-22 | 1954-11-17 | Vickers Armstrongs Ltd | Improvements in gas turbine engine installations |
FR1079233A (fr) * | 1952-04-29 | 1954-11-26 | Rolls Royce | Perfectionnements aux dispositifs d'alimentation en combustible pour moteurs à turbine à gaz |
US2803110A (en) * | 1953-06-11 | 1957-08-20 | Keelavite Co Ltd | Hydraulic power drive for reciprocating members |
DE1020035B (de) * | 1955-01-29 | 1957-11-28 | Tolkien & Co | Kolbendampfmaschine mit vom Arbeitsdampf betaetigter Schiebersteuerung |
FR1180597A (fr) * | 1957-08-05 | 1959-06-05 | Air Equipement | Installation de compression d'air, plus particulièrement sur aéronefs |
US2942553A (en) * | 1958-05-09 | 1960-06-28 | Gen Motors Corp | Gas driven hydraulic actuator |
US3019735A (en) * | 1958-05-09 | 1962-02-06 | Gen Motors Corp | Gas driven hydraulic pump |
DE1528583A1 (de) * | 1965-05-20 | 1970-01-29 | Stahl U Appbau Hans Leffer Gmb | Hydraulisch oder pneumatisch kontinuierlich betaetigter Kolbenantrieb mit hin- und hergehender Bewegung,insbesondere doppeltwirkender Druckuebersetzer |
DE1782429A1 (de) * | 1968-08-27 | 1971-08-26 | Escher Wyss Gmbh | Anordnung zum Umsteuern der Axialbewegung von Schubboeden in Schubzentrifugen |
US3909159A (en) * | 1973-03-05 | 1975-09-30 | Garrett Corp | Variable displacement pump for gas turbine fuel management system |
US3909152A (en) * | 1973-09-27 | 1975-09-30 | United Aircraft Corp | Variable size bleed port for jet engines |
US4091613A (en) * | 1976-07-30 | 1978-05-30 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Independent power generator |
US4175701A (en) * | 1978-05-15 | 1979-11-27 | The Garrett Corporation | Aircraft spraying system and method |
-
1979
- 1979-09-06 DE DE19792936005 patent/DE2936005A1/de active Granted
-
1980
- 1980-08-22 EP EP80105002A patent/EP0025526B1/de not_active Expired
- 1980-09-05 CA CA000359705A patent/CA1162061A/en not_active Expired
- 1980-09-05 US US06/184,430 patent/US4400934A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3659417A (en) * | 1968-08-08 | 1972-05-02 | Daimler Benz Ag | Gas turbine unit for generating mechanical energy and compressed air |
US4182117A (en) * | 1978-01-09 | 1980-01-08 | Avco Corporation | Diffuser vane cusp bleed aperture with automatic ejector control device |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5285626A (en) * | 1992-03-20 | 1994-02-15 | Woodward Governor Company | Drive for main engine auxiliaries for an aircraft gas turbine engine |
US5784812A (en) * | 1994-07-13 | 1998-07-28 | O&K Orenstein & Koppel Ag | Method of controlling the positioning of an outfit tilting cylinder mounted on the descending lift frame of movable construction machines |
WO2010089769A2 (en) * | 2009-01-13 | 2010-08-12 | Dattatraya Rajaram Shelke | A device for transferring energy between fluids |
WO2010089769A3 (en) * | 2009-01-13 | 2011-06-30 | Dattatraya Rajaram Shelke | A device for transferring energy between fluids |
WO2012042533A2 (en) * | 2010-09-29 | 2012-04-05 | Dattatraya Rajaram Shelke | Device for transferring energy between two fluids |
WO2012042533A3 (en) * | 2010-09-29 | 2012-06-07 | Dattatraya Rajaram Shelke | Device for transferring energy between two fluids |
CN103615365A (zh) * | 2013-11-26 | 2014-03-05 | 浙江理工大学 | 一种集成阀式气驱液增压泵 |
CN103615365B (zh) * | 2013-11-26 | 2015-09-30 | 浙江理工大学 | 一种集成阀式气驱液增压泵 |
Also Published As
Publication number | Publication date |
---|---|
DE2936005C2 (de) | 1992-05-21 |
EP0025526A1 (de) | 1981-03-25 |
DE2936005A1 (de) | 1981-03-19 |
CA1162061A (en) | 1984-02-14 |
EP0025526B1 (de) | 1988-01-20 |
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Legal Events
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STCF | Information on status: patent grant |
Free format text: PATENTED CASE |